1vr&d1 industrial optimization: status and prospects g. vanderplaats vanderplaats research &...
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VR&D 1 1
INDUSTRIAL OPTIMIZATION: STATUS AND PROSPECTS
G. Vanderplaats
Vanderplaats Research & Development, Inc.
1767 S. 8th StreetColorado Springs, CO 80906
Ph. (719) 473-4611
Copyright VR&D 2004
www. vrand.com
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VR&D 2 2
• Minimize F(X) Objective Function
• Subject to (Such That);
Inequality Constraints
Equality Constraints
Side Constraints
F(X), gj(X) and hk(X) May be Linear, Nonlinear, Explicit, Implicit, but Should be Continuous with Continuous First Derivatives
GENERAL OPTIMIZATION GENERAL OPTIMIZATION PROBLEM STATEMENTPROBLEM STATEMENT
NiXXX
LkXh
MjXg
Uii
Li
k
j
,1
,10)(
,10)(
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VR&D 3 3
• Given Xq
• Update the Design by
Xq = Xq-1 + Sq Xq-1 + X
• Note that this is Very Close to the Traditional Design Process of Beginning with a Design and Modifying it
THE OPTIMIZATION PROCESSTHE OPTIMIZATION PROCESS
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VR&D 4 4
• 1948: SIMPLEX Method for Linear Programming
• 1950’s: Various Random Methods. Gradient Based Methods Developed in the Late 1950’s
• 1960’s: Sequential Unconstrained Minimization Techniques, Sequential Linear Programming, Feasible Directions Methods
• 1970’s: Enhanced Feasible Directions Methods, Multiplier Methods, Reduced Gradient Methods, Response Surface Approximations
• 1980’s: Variable Metric Methods, Sequential Quadratic Programming Methods
OPTIMIZATION ALGORITHMSOPTIMIZATION ALGORITHMS
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VR&D 5 5
• 1990’s: Genetic Algorithms, Simulated Annealing, New Interest in Sequential Unconstrained Minimization Techniques
• 2000’s: Particle Swarming, Advanced Sequential Unconstrained Minimization Techniques
• Largest Known Test Example– 500,000 Variables With 500,000 Active Constraints
• Largest Known Real Structural Optimization Problem– 250,000+ Thickness Variables with Frequency Constraints
– 2,000,000+ Topology Variables
OPTIMIZATION ALGORITHMSOPTIMIZATION ALGORITHMS
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VR&D 6 6
OPTIMIZATION PROBLEM SIZEOPTIMIZATION PROBLEM SIZE
0
100
1,000
10,000
1960 1970 1980 1990 2000 2010
# Des. Var.
Year
100,000
BIGDOT500,000VARIABLES
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VR&D 7 7
STRUCTURAL OPTIMIZATIONSTRUCTURAL OPTIMIZATION
• 1960 - Schmit combined optimization and analysis– 2Variables; 1/2 hour on IBM 653
• 1973 - Schmit et al introduced physics based approximations• 1986 - Vanderplaats et al developed 2nd generation
approximations• 1975 - 1989 Optimization added to commercial structural
analysis programs• 1984 - 2000 General purpose engineering optimization
software• Optimization software used by engineers is usually created by
engineers
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VR&D 8 8
G . N . V a nd erp l aats
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VR&D 9 9
• 1975
OPTIMIZATION WORKSOPTIMIZATION WORKS
C O M B AT
M IS SIO N
I N ITIA L O PT IM U M
SUPERSO NIC CRUISE AIRCRAFT
S OL VED B Y T H E AC SY N T PR O GR A M
5 D ES IGN V AR IA BLE S, 2 PER F O R M AN C E C ON S T R AIN T S
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VR&D 10 10
• 1975
OPTIMIZATION WORKSOPTIMIZATION WORKS
SU PER SON IC CRU ISE AIR CRAFT
TRAD E - OFF STU DY
{1.0
0.9
0.8
0
0.6
0.8
1.0
1.2
1.4
3 4 5 6 7 8
S UST AINE D LOA D FAC TO R AT M = 0 .9
RE
LA
TIV
E M
AS
S
NOMINALDESIG N
TECHNO LO GYFACTO R
CO NVENTIONAL
ADVANCED
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VR&D 11 11
• 1976: A Two Hour Optimization Study
OPTIMIZATION WORKSOPTIMIZATION WORKS
STO L AIRCRAFT TAKEO FF
CO N VEN TIO N AL: W = WG0
VARIATIO N AL CALCU LU S: W = 2.5WG0
N U M ERICAL O PTIM IZATIO N : W = 1.2WG0
20gFlig htSp e e d
2g
500 ft/m inC lim b
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VR&D 12 12
• 1978: Today Called “Response Surface Method”
OPTIMIZATION WORKSOPTIMIZATION WORKS
HIGH SPEED AIRFOIL OPTIMIZATION
INIT IAL SHAP E
O PT IMU M: M AXIM IZE LIF T WIT H DRAG & M O ME NT CO NST RAINT S
O PT IMUM : MINIM IZE D RAG W ITH LIF T & M O ME NT CO NS TRAINT S
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VR&D 13 13
• It Has Been Working For Many Years– The Above Examples are 25-30 Years Old!
• The Aircraft Example was a 1 Man Month Study, Verified by a One Year, $250,000 Study by a Commercial Aircraft Company
• The Aircraft Take-off Example Solved a Ph.D. Problem that Took Over a Year and Got the Wrong Answer
• The Airfoil Example Produced a Design Almost Identical to a Multi Year Wind Tunnel Study
• It is Not Debatable that Optimization is Useful
OPTIMIZATION WORKSOPTIMIZATION WORKS
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VR&D 14 14
• Use Approximations to Avoid Many Calls to the FEA– Optimizer Never Actually Calls the Finite Element Analysis
MODERN STRUCTURAL MODERN STRUCTURAL OPTIMIZATIONOPTIMIZATION
CONTROLPROGRAM
SENSITIVITYANALYSIS
OPTIMIZER
APPROXIMATEPROBLEM
GENERATORAPPROXIMATE
ANALYSIS
FEMANALYSIS
CONSTRAINTSCREENING
INNER LOOP
OUTER LOOP
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VR&D 15 15
• Criteria– Find a Very Good Optimum Quickly
– Use as Few Full Finite Element Analyses as Possible
• Basis for Criteria– Each Analysis Requires a Full Finite Element Solution
• This Can be Very Expensive
• Cost– About 10-15 Times the Cost of One Analysis
• This Estimate Assumes Analytic Gradients are Calculated
• It Also Assumes 2nd Generation Approximation Techniques are Used
THE COST OF STRUCTURAL THE COST OF STRUCTURAL OPTIMIZATIONOPTIMIZATION
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VR&D 16 16
• Modern Structural Optimization Converts the Original Design Problem to an Approximate Form Before Calling the Optimizer– Optimizer Calls Approximate Analysis Many Times
– Usually About Ten Detailed Finite Element Analyses are Needed• 95% of CPU Time is Analysis and Gradient (Sensitivity) Calculations
• Finite Element Models of the Order of 1,000,000 Degrees of Freedom are Becoming Common
• Problems in Excess of 250,000 Design Variables Have Been Solved by the GENESIS Program
STRUCTURAL OPTIMIZATIONSTRUCTURAL OPTIMIZATION
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VR&D 17 17
Rocket Curved Stiffened Panel
• Minimize mass of the aluminum curved stiffened panel
• Eight design variables:– Thickness of skin and stiffeners– Stiffener web height– Stiffener flange widths
• Frequency constraint > 45 Hz (Initially = 23 HZ)
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VR&D 18 18
Panel Optimization Results
• Frequency constraint is satisfied
• 30% mass reduction
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VR&D 19 19
Spinning Disk
• Axi-symmetric structure w.r.t. the Y axis• Centrifugal load resulting from a 12 Hz rotation• Two material structure
– Outer part is aluminum– Inner part is steel
x
y
Aluminum
Steel
100 mm
30 mm
2 mm
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VR&D 20 20
Spinning Disk Results
• 26% 26% Mass reduction
• Lowest natural frequency increased• Maximum stress reduced
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VR&D 21 21
Shape Optimization of a Pin
• Pin must carry a specified load
• Nonlinear contact problem solved using ABAQUS
• Three materials: pin, adhesive,solid base
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VR&D 22 22
Shape Optimization of a Pin
• Minimize maximum stress inthe solid base
• Constraints: displacement, stress
• Nine shape design variables
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VR&D 23 23
Shape Optimization of a Pin
• Maximum stress reduction: 11%11%
• Improved stress distribution
• Small changes in the initial shape
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VR&D 24 24
Optimize Heat Sink Shape (for PC processor)
Minimize: Mass
Subject To:
– min heat dissipation into the air
– max tO in thyristor
– max tO in chassis
Analysis:Flux2D - FE based package
for the analysis of
electromagnetic and thermal
devices and processes
VisualDOC/FLUX2D
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VR&D 25 25
Initial design Final design
Design variables:height of the baseheight and width of fins
Result:Result:47% mass reduction47% mass reductionall constraints satisfiedall constraints satisfied
Initial design was choseninfeasible for demo
Final design looks likenormal heat sink in PC
VisualDOC/FLUX2D
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VR&D 26 26
CORE+
CO
IL
- C
OIL
GAP
C-Shaped Magnetic Circuit FLUX2D Model
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VR&D 27 27
CORE
GAP
X
Y
Flux Density in GAP of Initial Design
- Initial geometry gives a non-uniform magnetic field (flux) in the air gap- Optimize the geometry of the gap to give a prescribed point flux, or uniform flux along the length of the gap
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VR&D 28 28
Pt. 1
Pt. 2Pt. 3 Pt. 4
Pt. 5
Pt. 6GAP
Change the Y coordinates of points 1-6 and X coordinates of points 2-5 in order to produce a uniform flux density of 0.6 Tesla within the gap. Note: Symmetry Imposed
Case 3: Optimum Flux Density in GAP
Minimize the sum of the squares of the error (SSE) at 200 points
CORE
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VR&D 29 29
Flux Density Variation in GAP of Optimized Designs
Designing all X and Y coordinates produces the flattest flux density as shown in case 3 above
Magnetic Flux Density in Gap
0.57
0.62
0.67
0.72
0.77
0 2 4 6 8 10
X (mm)
Flu
x (
Te
sla
)
Case 1
Case 2
Case 3
Orig
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VR&D 30 30
Transport Aircraft Wing
• Multilevel Optimization– System level: configuration
design variables
– Disciplinary level: aerodynamic analysis and structural analysis / Optimization
• Multidisciplinary Optimization with both aerodynamics & structures components
• Maximize the range for constant gross weight
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VR&D 31 31
Disciplinary Issues
• Interaction between system level and structural sub-optimization is complexcomplex
• Must converge on loads and displacements– Changes in aerodynamic shape at the system level
affect the structural geometry
Aerodynamic loads deform the structure
Structural deformations affect aerodynamic loads
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VR&D 32 32
Transport Aircraft Wing
initial
final
Parameter Initial Value Direct Optimization
Optimization using RS
Range (n.mi.) 5,000 6,342 6,403 25% increase Depth to chord ratio
0.12 0.14 0.14 Aspect ratio 6.86 5.92 5.88
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VR&D 33 33
Airfoil Optimization
• NACA 4-digit airfoil• Design variables:
– maximum mean line camber as fraction of chord (m)
– chordwise position of maximum camber (p)– maximum thickness as fraction of chord (t)– Angle of attack ()
• Maximize ratio of Lift/Drag.• Use GAMBIT/FLUENT for geometric/flow
modeling.
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VR&D 34 34
Optimization ResultsPressure Distribution
Initial design
Final design
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VR&D 35 35
Equivalent Material Properties
• Reduce the size of the Heat Exchanger FE model by replacing air fin shell elements with equivalent anisotropic solid elements(not able to run the modal analysis on available computers)
Match the frequency anddisplacement responses
Analysis:Genesis - FE analysis and
Optimization code
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VR&D 36 36
Equivalent Material ...
Original Configuration
Equivalent ConfigurationOverall mode shapes not changed
3% error in frequencies5% error in displacements1 million DOF reduction in FE model size1 million DOF reduction in FE model size
1st twist mode
Diagonal elements of 6x6material property matrix [G] were adjusted:
}{ ] [ }{ G
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VR&D 37 37
Number of Elements=60,704 Number of Elements=60,704
Number of Design Variables = 60,704 Number of Design Variables = 7936
Traditional Results Casting Results
Design variables reduced by 87%
Manufacturing Constraints
No constraints added
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VR&D 38 38
Topometry Optimization Example:Where to Reinforce?
•Objective:
– Maximize Natural frequencies
•Constraints:
– Mass
•Design Variables: 34,560
– Each Element thickness
Added Mass (Kg)
Increased Frequency (Hz)
Maximizig First
Torsion Frequency
Maximizig First
BendingFrequency
Maximizig Averageof two
Frequencis
2.64 4.81 6.42 4.24
7.32 7.56 9.89 6.41
15.06 9.66 12.15 12.58
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VR&D 39 39
COMMERCIAL SOFTWARECOMMERCIAL SOFTWARE
Company Web AddressGeneral
OptimizationStructural
OptimizationAltair Engineering www.altair.com HyperOpt OptiStruct
Ansys www.ansys.com - - - Ansys-CADOE
Engineous Software www.engineous.com iSIGHT - - -
MSC Software www.mscsoftware.com - - - MSC.Nastran
Noesis www.noesissolutions.com Optimus - - -
Opttek www.optteck.com OptQuest - - -
Oculus Technologies www.oculustech.com CO - - -
Phoenix Integration www.phoenix-int.com Model Center - - -
UGS PLM www.ugs.com - - - NX.Nastran
Vanderplaats R&D www.vrand.com VisualDOC, DOT, BIGDOT
GENESIS
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VR&D 40 40
FUTURE PROSPECTSFUTURE PROSPECTS
• Schmit – 1980s– “I believe optimization has a future because people
think they can make money on it”
• Just as Spreadsheets are Routinely Used by Accounts
• Just as Word Processors are Routinely Used by Secretaries
• So Should Optimization be Used by Engineers
• Optimization Will be Widely Used when Management Understands the Enormous Benefit
• Progress Is Made One Retirement at a Time
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VR&D 41 41
SUMMARYSUMMARY
• Optimization Technology is Well Developed• For General Applications
– We Can Couple Almost Any Analysis With Optimization
• For Structural Optimization– Technology is Very Advanced
– Find an Optimum Using Only About 10 Finite Element Analyses
• Optimization is the Most Powerful Design Improvement Tool Available Today